Abstract: A tube for interconnecting combustors (11, 12) in a gas turbine combustion system for ignition purposes. The tube comprises three elements: two outer tube sections (15, 17) connected to respective combustors (11, 12) and an inner tube section (16) coupling the two outer sections (15, 17). The ends (20) of the inner tube section (16) protrude somewhat into the outer sections so that air inlet through holes (19) in the outer sections in the vicinity of the two couplings produces cooling air flow (14) adjacent the inner surface of the tube in opposite directions. The bi-directional nature of the air flow (14) substantially prevents any mechanism by which hot combustion gases (10) are carried between the two combustors by the cooling air, thus providing effective tube cooling and prolonging the life of the tube.

Abstract: A combustor for a gas turbine engine. The combustor employs an array of fuel injectors arranged across and in the mouth plane of the combustor flame tube. Each injector has a baffle plate through which the injector nozzle projects, the baffle plate having axial holes for atomization air to intercept and atomize radial fuel jets from the injector nozzle. Cooling of the flame tube is performed by full coverage impingement and effusion without disturbing the cooling film by entry and penetration of transverse air jets. Flame stabilization is achieved under all required operating conditions by the radial-fuel/axial-air atomization in conjunction with the baffle plates. Comprehensive combustion mixing and dilution is achieved by the uniformly distributed supply of up to 90% of the total air supplied to the combustor around and through the baffle plates.